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FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 63-100 AIRFOIL (fx63100-il)
Reynolds number: 500,000
Max Cl/Cd: 121.72 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63100-il-500000.txt
Download as CSV file: xf-fx63100-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-100 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2731   0.09464   0.09253  -0.0358   1.0000   0.0243
  -9.500  -0.2800   0.09099   0.08891  -0.0360   1.0000   0.0253
  -9.250  -0.2934   0.08614   0.08410  -0.0381   0.9997   0.0260
  -9.000  -0.2870   0.08026   0.07823  -0.0426   0.9981   0.0260
  -8.750  -0.2847   0.07343   0.07141  -0.0461   0.9962   0.0265
  -8.500  -0.2688   0.07007   0.06804  -0.0482   0.9945   0.0270
  -8.250  -0.2572   0.06601   0.06399  -0.0512   0.9917   0.0274
  -8.000  -0.2454   0.06163   0.05961  -0.0549   0.9883   0.0281
  -7.750  -0.3540   0.04497   0.04262  -0.0923   0.9799   0.0214
  -7.500  -0.3183   0.02607   0.02250  -0.1167   0.9735   0.0189
  -7.250  -0.2810   0.02054   0.01619  -0.1227   0.9700   0.0198
  -7.000  -0.2456   0.01834   0.01354  -0.1254   0.9658   0.0207
  -6.750  -0.2091   0.01654   0.01156  -0.1283   0.9632   0.0221
  -6.500  -0.1720   0.01598   0.01095  -0.1306   0.9611   0.0236
  -6.250  -0.1370   0.01500   0.00978  -0.1323   0.9573   0.0252
  -6.000  -0.1034   0.01362   0.00822  -0.1338   0.9521   0.0269
  -5.750  -0.0669   0.01295   0.00754  -0.1358   0.9489   0.0289
  -5.500  -0.0282   0.01253   0.00705  -0.1381   0.9463   0.0316
  -5.250   0.0050   0.01152   0.00597  -0.1395   0.9389   0.0343
  -5.000   0.0430   0.01102   0.00545  -0.1417   0.9342   0.0372
  -4.750   0.0789   0.01073   0.00509  -0.1433   0.9275   0.0401
  -4.500   0.1167   0.00990   0.00422  -0.1456   0.9207   0.0440
  -4.250   0.1515   0.00960   0.00388  -0.1470   0.9120   0.0478
  -3.750   0.2183   0.00891   0.00304  -0.1493   0.8900   0.0565
  -3.500   0.2482   0.00876   0.00281  -0.1495   0.8776   0.0613
  -3.250   0.2785   0.00850   0.00253  -0.1500   0.8670   0.0726
  -3.000   0.3088   0.00825   0.00230  -0.1505   0.8575   0.0957
  -2.750   0.3381   0.00802   0.00213  -0.1508   0.8477   0.1258
  -2.500   0.3698   0.00741   0.00196  -0.1522   0.8391   0.2754
  -2.250   0.3991   0.00720   0.00194  -0.1525   0.8296   0.3645
  -2.000   0.4280   0.00712   0.00191  -0.1527   0.8208   0.4040
  -1.750   0.4569   0.00705   0.00188  -0.1528   0.8120   0.4386
  -1.500   0.4856   0.00695   0.00191  -0.1529   0.8029   0.4862
  -1.000   0.5423   0.00696   0.00204  -0.1528   0.7852   0.5784
  -0.750   0.5705   0.00703   0.00207  -0.1527   0.7768   0.6009
  -0.500   0.5986   0.00707   0.00210  -0.1525   0.7676   0.6169
  -0.250   0.6265   0.00711   0.00214  -0.1523   0.7587   0.6336
   0.000   0.6544   0.00717   0.00218  -0.1521   0.7497   0.6493
   0.250   0.6822   0.00721   0.00223  -0.1520   0.7403   0.6618
   0.500   0.7099   0.00728   0.00228  -0.1517   0.7311   0.6761
   0.750   0.7372   0.00733   0.00233  -0.1514   0.7197   0.6889
   1.000   0.7644   0.00739   0.00238  -0.1511   0.7058   0.6991
   1.250   0.7916   0.00746   0.00242  -0.1507   0.6915   0.7095
   1.500   0.8187   0.00753   0.00248  -0.1504   0.6789   0.7186
   1.750   0.8461   0.00761   0.00256  -0.1502   0.6672   0.7282
   2.000   0.8732   0.00771   0.00264  -0.1499   0.6540   0.7384
   2.250   0.8999   0.00780   0.00272  -0.1495   0.6389   0.7487
   2.500   0.9266   0.00790   0.00282  -0.1491   0.6230   0.7598
   2.750   0.9532   0.00802   0.00293  -0.1487   0.6055   0.7717
   3.000   0.9790   0.00816   0.00304  -0.1482   0.5832   0.7841
   3.250   1.0043   0.00833   0.00316  -0.1476   0.5564   0.7983
   3.500   1.0291   0.00854   0.00332  -0.1468   0.5276   0.8151
   3.750   1.0530   0.00875   0.00349  -0.1460   0.4996   0.8359
   4.250   1.0918   0.00897   0.00376  -0.1421   0.4508   1.0000
   4.500   1.1178   0.00934   0.00401  -0.1418   0.4243   1.0000
   4.750   1.1430   0.00976   0.00429  -0.1414   0.3934   1.0000
   5.000   1.1678   0.01020   0.00458  -0.1410   0.3588   1.0000
   5.250   1.1916   0.01073   0.00492  -0.1404   0.3172   1.0000
   5.500   1.2143   0.01138   0.00533  -0.1396   0.2706   1.0000
   5.750   1.2365   0.01209   0.00580  -0.1388   0.2280   1.0000
   6.000   1.2590   0.01276   0.00629  -0.1381   0.1933   1.0000
   6.250   1.2811   0.01347   0.00682  -0.1373   0.1595   1.0000
   6.750   1.3216   0.01524   0.00812  -0.1351   0.0831   1.0000
   7.000   1.3420   0.01609   0.00885  -0.1340   0.0646   1.0000
   7.250   1.3631   0.01684   0.00955  -0.1329   0.0550   1.0000
   7.500   1.3857   0.01737   0.01012  -0.1321   0.0507   1.0000
   7.750   1.4069   0.01802   0.01077  -0.1310   0.0470   1.0000
   8.000   1.4264   0.01883   0.01161  -0.1297   0.0439   1.0000
   8.250   1.4478   0.01939   0.01224  -0.1287   0.0421   1.0000
   8.500   1.4681   0.02003   0.01293  -0.1276   0.0401   1.0000
   8.750   1.4865   0.02082   0.01373  -0.1262   0.0381   1.0000
   9.000   1.4983   0.02213   0.01511  -0.1238   0.0358   1.0000
   9.250   1.5173   0.02274   0.01581  -0.1225   0.0347   1.0000
   9.500   1.5335   0.02348   0.01663  -0.1207   0.0334   1.0000
   9.750   1.5468   0.02429   0.01750  -0.1185   0.0320   1.0000
  10.000   1.5580   0.02521   0.01846  -0.1161   0.0305   1.0000
  10.250   1.5608   0.02679   0.02010  -0.1127   0.0290   1.0000
  10.500   1.5683   0.02812   0.02154  -0.1100   0.0278   1.0000
  10.750   1.5812   0.02901   0.02254  -0.1082   0.0268   1.0000
  11.000   1.5918   0.03011   0.02373  -0.1062   0.0255   1.0000
  11.250   1.6015   0.03130   0.02498  -0.1043   0.0244   1.0000
  11.500   1.6073   0.03289   0.02662  -0.1022   0.0233   1.0000
  11.750   1.6040   0.03560   0.02942  -0.0994   0.0222   1.0000
  12.000   1.6165   0.03665   0.03060  -0.0982   0.0213   1.0000
  12.250   1.6258   0.03809   0.03215  -0.0969   0.0203   1.0000
  12.500   1.6334   0.03975   0.03391  -0.0956   0.0194   1.0000
  12.750   1.6400   0.04156   0.03579  -0.0944   0.0187   1.0000
  13.000   1.6424   0.04392   0.03821  -0.0932   0.0180   1.0000
  13.250   1.6371   0.04739   0.04179  -0.0918   0.0173   1.0000
  13.500   1.6424   0.04964   0.04418  -0.0911   0.0169   1.0000
  13.750   1.6458   0.05218   0.04687  -0.0905   0.0163   1.0000
  14.000   1.6482   0.05491   0.04973  -0.0901   0.0157   1.0000
  14.250   1.6505   0.05772   0.05264  -0.0899   0.0152   1.0000
  14.500   1.6516   0.06078   0.05579  -0.0899   0.0147   1.0000
  14.750   1.6515   0.06409   0.05919  -0.0902   0.0143   1.0000
  15.000   1.6464   0.06828   0.06349  -0.0906   0.0139   1.0000
  15.250   1.6344   0.07368   0.06903  -0.0913   0.0136   1.0000
  15.500   1.6319   0.07787   0.07339  -0.0923   0.0133   1.0000
  15.750   1.6268   0.08259   0.07828  -0.0935   0.0131   1.0000
  16.000   1.6206   0.08769   0.08355  -0.0951   0.0128   1.0000
  16.250   1.6131   0.09313   0.08916  -0.0970   0.0126   1.0000
  16.500   1.6050   0.09885   0.09503  -0.0993   0.0123   1.0000
  16.750   1.5964   0.10480   0.10114  -0.1019   0.0121   1.0000
  17.000   1.5884   0.11082   0.10731  -0.1047   0.0119   1.0000
  17.250   1.5786   0.11730   0.11394  -0.1079   0.0118   1.0000
  17.500   1.5688   0.12391   0.12069  -0.1115   0.0116   1.0000
  17.750   1.5598   0.13048   0.12739  -0.1152   0.0114   1.0000
  18.000   1.5504   0.13724   0.13428  -0.1191   0.0113   1.0000
  18.250   1.5415   0.14400   0.14116  -0.1233   0.0112   1.0000
  18.500   1.5278   0.15202   0.14934  -0.1284   0.0111   1.0000
  18.750   1.5189   0.15904   0.15647  -0.1330   0.0110   1.0000
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